FR2840358A1 - METHOD AND SYSTEM FOR DETECTING ROTOR DAMAGE OF AN AIRCRAFT ENGINE - Google Patents

METHOD AND SYSTEM FOR DETECTING ROTOR DAMAGE OF AN AIRCRAFT ENGINE Download PDF

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Publication number
FR2840358A1
FR2840358A1 FR0206530A FR0206530A FR2840358A1 FR 2840358 A1 FR2840358 A1 FR 2840358A1 FR 0206530 A FR0206530 A FR 0206530A FR 0206530 A FR0206530 A FR 0206530A FR 2840358 A1 FR2840358 A1 FR 2840358A1
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France
Prior art keywords
vector
vibration
flight
module
threshold value
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Granted
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FR0206530A
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French (fr)
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FR2840358B1 (en
Inventor
Patrick Comperat
Philippe Even
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Safran Aircraft Engines SAS
Original Assignee
SNECMA Services SA
SNECMA Moteurs SA
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Application filed by SNECMA Services SA, SNECMA Moteurs SA filed Critical SNECMA Services SA
Priority to FR0206530A priority Critical patent/FR2840358B1/en
Priority to ES03291230T priority patent/ES2269942T3/en
Priority to DE60307926T priority patent/DE60307926T2/en
Priority to EP03291230A priority patent/EP1367226B1/en
Priority to RU2003116164/06A priority patent/RU2320969C2/en
Priority to JP2003149102A priority patent/JP4111869B2/en
Priority to UA2003054893A priority patent/UA82462C2/en
Priority to CA2430153A priority patent/CA2430153C/en
Priority to US10/445,935 priority patent/US6918747B2/en
Publication of FR2840358A1 publication Critical patent/FR2840358A1/en
Application granted granted Critical
Publication of FR2840358B1 publication Critical patent/FR2840358B1/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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Classifications

    • GPHYSICS
    • G01MEASURING; TESTING
    • G01HMEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
    • G01H1/00Measuring characteristics of vibrations in solids by using direct conduction to the detector
    • G01H1/003Measuring characteristics of vibrations in solids by using direct conduction to the detector of rotating machines
    • G01H1/006Measuring characteristics of vibrations in solids by using direct conduction to the detector of rotating machines of the rotor of turbo machines
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04Antivibration arrangements
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00Testing of engines
    • G01M15/04Testing internal-combustion engines
    • G01M15/12Testing internal-combustion engines by monitoring vibrations
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00Testing of engines
    • G01M15/14Testing gas-turbine engines or jet-propulsion engines

Abstract

L'invention concerne la détection d'endommagement de rotor d'un moteur d'aéronef comprenant des moyens de mesure de vibration et de vitesse du rotor pendant un vol déterminé et comportant les étapes suivantes :- acquisition (10) de données relative à la vitesse du rotor ainsi qu'à l'amplitude et à la phase des vibrations du rotor à partir desdits moyens de mesure,- calcul (20, 30, 40) d'un vecteur vibration moyen sur un intervalle de vitesse de rotor déterminé à partir desdites données acquises,- calcul (61) d'une différence vectorielle entre le vecteur vibration moyen dudit vol déterminé et le vecteur vibration moyen d'un vol de référence pour un même intervalle de vitesse rotor,- comparaison (90) du module de ladite différence vectorielle avec une valeur seuil prédéterminé, et- émission d'un signal d'alerte lorsque le module de ladite différence vectorielle excède une valeur seuil prédéterminée.The invention relates to the detection of rotor damage of an aircraft engine comprising means for measuring vibration and rotor speed during a given flight and comprising the following steps: acquisition (10) of data relating to the rotor speed as well as amplitude and phase of rotor vibration from said measuring means; - calculation (20, 30, 40) of a mean vibration vector over a rotor speed interval determined from of said acquired data, - calculation (61) of a vector difference between the average vibration vector of said determined flight and the average vibration vector of a reference flight for the same rotor speed interval, - comparison (90) of the module of said vector difference with a predetermined threshold value, and- emission of an alert signal when the module of said vector difference exceeds a predetermined threshold value.

Description

moteur peut tourner dans l'un ou l'autre sens de rotation.motor can rotate in either direction of rotation.

Arriere-plan de ['invention L'invention concerne la detection d'endommagement de rotor d'un  BACKGROUND OF THE INVENTION The invention relates to the detection of rotor damage of a

moteur d'aeronef.aircraft engine.

La reglementation en vigueur dans ['aviation civile, impose de surveiller les vibrations de moteurs d'avions. Cette surveillance s'effectue  The regulations in force in civil aviation require the monitoring of aircraft engine vibrations. This surveillance is carried out

generalement au moyen d'accelerometres.  usually by means of accelerometers.

Le signal issu de chaque accelerometre est d'abord traite afin d'en extraire les composantes frequentielles correspondent aux vitesses de rotation des rotors des etages basse pression et haute pression. L'amplitude de ces composantes est renvoyee en temps reel au cockpit et quelques valeurs pertinentes vent stockees pour une exploitation ulterieure. En genera le. 5 a 10 valeurs pa r vol dans des conditions stabil isees predefin ies  The signal from each accelerometer is first processed in order to extract the frequency components corresponding to rotational speeds of the rotors of the low pressure and high pressure stages. The amplitude of these components is returned in real time to the cockpit and some relevant values are stored for later use. In general. 5 to 10 values per flight in pre-defined stable conditions

vent stockes.stored wind.

Malheureusement, il arrive qu'un rotor d'un moteur d'avion soit endommage, comme par exemple, I'arrachement d'aubes sans que  Unfortunately, it happens that a rotor of an airplane engine is damaged, for example, the tearing of blades without

I'evenement soit decele du fait du peu de donnees recueillies.  The event is detected due to the paucity of data collected.

Aussi, il existe done un besoin a*uel d'un systeme qui permette sans erreurs la detection de ltendommagement du rotor d'un moteur d'aeronef. Objet et resume de ['invention L'invention a pour but de fournir un procede de detection d'endommagement de rotor d'un moteur d'aeronef, afin de garantir le bon  Also, there is therefore a need for a system which makes it possible without errors to detect damage to the rotor of an aircraft engine. OBJECT AND SUMMARY OF THE INVENTION The object of the invention is to provide a method for detecting rotor damage of an aircraft engine, in order to guarantee the proper

fonctionnement du moteur et la securite de l'avion.  engine operation and the safety of the aircraft.

Un autre but est de fournir un bon diagnostique dans les meilleurs  Another goal is to provide a good diagnosis in the best

delais afin d'avoir 1'equipe de maintenance adaptee au type du probleme.  time to have the maintenance team adapted to the type of the problem.

Encore un autre but est la realisation d'une maintenance preventive.  Yet another goal is the realization of preventive maintenance.

Ces buts vent atteints grace a un procede de detection d'endommagement de rotor d'un moteur d'aeronef comprenant des moyens de mesure de vibration et de vitesse du rotor pendant un vol determine, et comportant les etapes suivantes: - acquisition de donnees relative a la vitesse du rotor ainsi qu'a ['amplitude et 3 la phase des vibrations du rotor a partir desdits moyens de mesures, - calcul d'un vecteur vibration moyen sur un intervalle de vitesse de rotor determine 3 partir desdites donnees acquises, - calcul d'une difference vectorielle entre le vecteur vibration moyen audit vol determine et le vecteur vibration moyen d'un vol de reference pour un meme intervalle de vitesse rotor, - comparaison du module de ladite difference vectorielle avec une valeur seuil predetermine, et - emission d'un signal d'alerte lorsque le module de ladite  These aims are achieved by a method of detecting rotor damage of an aircraft engine comprising means for measuring vibration and rotor speed during a given flight, and comprising the following steps: - acquisition of relative data at the rotor speed and at the amplitude and phase of the rotor vibrations from said measuring means; calculating a mean vibration vector over a rotor speed interval determined from said acquired data; calculating a vector difference between the average vibration vector at said determined flight and the average vibration vector of a reference flight for the same rotor speed interval, - comparing the modulus of said vector difference with a predetermined threshold value, and - emission an alert signal when the module of the

difference ve*orielle excede une valeur seuil predeterminee.  vertical difference exceeds a predefined threshold value.

Le procede de detection selon ['invention, peut aussi comporter les etapes suivantes: - calcul d'une deuxieme difference vectorielle entre chaque vecteur vibration audit vol determine et le vecteur vibration moyen d'un vol de reference pour un meme intervalle de vitesse rotor, - calcul d'un module de ladite deuxieme difference vectorielle associee a chaque vecteur vibration afin de choisir un plus grand module, - comparaison audit plus grand module avec la valeur seuil predeterminee, et - emission d'un signal d'alerte lorsque ledit plus grand module  The detection method according to the invention may also comprise the following steps: calculating a second vector difference between each vibration vector at said determined flight and the mean vibration vector of a reference flight for the same rotor speed interval, calculating a module of said second vector difference associated with each vibration vector in order to choose a larger module, comparing said larger module with the predetermined threshold value, and transmitting an alert signal when said larger one module

excede la valeur seuil predeterminee.  exceeds the predetermined threshold value.

De meme, le procede de detection selon ['invention, peut aussi comporter caicul d'une troisieme difference vectorielle entre chaque vecteur vibration audit vol determine et le vecteur vibration moyen audit vol determine a un meme intervalle de vitesse rotor, - calcul d'un module de ladite troisieme difference vectorielle associee a chaque vecteur vibration afin de choisir un plus grand module, - comparaison audit plus grand module avec la valeur seuil predeterminee, et - emission d'un signal d'alerte lorsque ledit plus grand module  Likewise, the detection method according to the invention may also comprise a third vector difference between each vibration vector at said determined flight and the average vibration vector at said determined flight at the same rotor speed interval. module of said third vector difference associated with each vibration vector in order to choose a larger module, - comparison with said larger module with the predetermined threshold value, and - emission of an alert signal when said larger module

excede la valeur seuil predeterminee.  exceeds the predetermined threshold value.

Selon un premier mode de realisation, lesdites etapes de calcul, de  According to a first embodiment, said calculation steps,

comparaison et d'emission vent realisees 3 I'issue audit vol determine.  comparison and transmission carried out at the end of said determined flight.

Selon un second mode de realisation, le procede de detection est  According to a second embodiment, the detection method is

realise en cours audit vol determine.  performs in progress at said determined flight.

Selon une premiere particularite de ['invention, le vol de reference  According to a first feature of the invention, the reference flight

correspond au vol precedent audit vol determine.  corresponds to the previous flight at said determined flight.

Selon une seconde particularite de ['invention, le vol de reference  According to a second feature of the invention, the reference flight

correspond a un vol associe a un moteur standard de reference.  corresponds to a flight associated with a standard reference engine.

Ava ntageuse m ent, le procede sel on ['invention com porte u ne eta pe de mise a jour des vecteurs moyens du vol reference a partir des donnees audit vol determine lorque le module ou le plus grand module de la difference  With the apparatus, the method of the invention includes updating the average vectors of the reference flight from the data of said determined flight when the module or the largest module of the difference

vectorielle n'excede pas la valeur seuil predeterminee.  vector does not exceed the predefined threshold value.

L'amplitude audit intervalle de vitesse rotor determine correspond  The amplitude at said determined rotor speed interval corresponds

a une valeur comprise entre 1% et 10% de la vitesse nominale du rotor.  has a value between 1% and 10% of the rated speed of the rotor.

La valeur seuil est predeterminee selon ltemplacement du moyen de detection de vibration et correspond a une valeur comprise entre 2 mils et mils. L'invention a aussi pour but de fournir un systeme de detection d'endommagement de rotor d'un moteur d'aeronef permettant la mise en  The threshold value is predetermined according to the location of the vibration detection means and corresponds to a value of between 2 mils and mils. Another object of the invention is to provide a system for detecting rotor damage of an aircraft engine enabling the implementation of

oeuvre du procede defini ci-avant.of the process defined above.

Ce but est atteint grace a systeme de detection d'endommagement de rotor d'un moteur d'aeronef muni des moyens de mesure de vibration et de vitesse du rotor pendant un vol determine, et comprenant: - un moyen d'acquisition de donnees relative a la vitesse du rotor ainsi qu'a ['amplitude et a la phase des vibrations du rotor a partir desdits moyens de mesures, - un moyen de caicul d'un vecteur vibration moyen sur un intervalle de vitesse de rotor determine a partir desdites donnees acquises, - un moyen de calcul d'une difference vectorielle entre le vecteur vibration moyen audit vol determine et le vecteur vibration moyen d'un vol de reference pour un meme intervalle de vitesse rotor, - un moyen de comparaison du module de ladite difference vectorielle avec une valeur seuil predetermine, et - un moyen d'emission d'un signal d'alerte lorsque le module de  This object is achieved by the rotor damage detection system of an aircraft engine provided with means for measuring vibration and rotor speed during a given flight, and comprising: a relative data acquisition means at the speed of the rotor as well as the amplitude and the phase of the rotor vibrations from said measuring means, a means of caicul of a mean vibration vector over a rotor speed interval determined from said data acquired, - means for calculating a vector difference between the average vibration vector at said determined flight and the average vibration vector of a reference flight for the same rotor speed interval, - means for comparing the module of said vector difference with a predetermined threshold value, and - means for transmitting an alert signal when the module of

ladite difference vectorielie excede une valeur seuil predeterminee.  said vector difference exceeds a predetermined threshold value.

Le systeme de detection selon ['invention peut aussi comporter: - un moyen de calcul d'une deuxieme difference entre chaque vecteur vibration audit vol determine et le vecteur vibration moyen d'un vol de reference pour un meme intervalle de vitesse rotor, - un moyen de calcul d'un module de ladite deuxieme difference vectorielle associee a chaque vecteur vibration et de choisir un plus grand module, - un moyen de comparaison audit plus grand module avec la valeur seuil predeterminee, et - un moyen d'emission d'un signal d'alerte lorsque ledit plus grand  The detection system according to the invention may also comprise: a means for calculating a second difference between each vibration vector at said determined flight and the average vibration vector of a reference flight for the same rotor speed interval; means for calculating a module of said second vector difference associated with each vibration vector and for choosing a larger module; - means for comparing said largest module with the predetermined threshold value; and - means for transmitting a warning signal when said larger

module excede la valeur seuil predeterminee.  module exceeds the predetermined threshold value.

De meme le systeme de detection selon ['invention peut aussi comporter: un moyen de calcul d'une troisieme difference vectorielle entre chaque vecteur vibration audit vol determine et le vecteur vibration moyen audit vol determine a un meme intervalle de vitesse rotor, - un moyen de calcul d'un module de ladite troisieme difference vectorielle associee a chaque vecteur vibration afin de choisir un plus grand module, - un moyen de comparaison audit plus grand module avec la valeur seuil predeterminee, et - un moyen d'emission d'un signal d'alerte lorsque ledit plus grand  Similarly, the detection system according to the invention may also comprise: means for calculating a third vector difference between each vibration vector at said determined flight and the average vibration vector at said determined flight at a same rotor speed interval; calculating a module of said third vector difference associated with each vibration vector in order to choose a larger module; - means for comparing said largest module with the predetermined threshold value; and - means for transmitting a signal. alert when said larger

module excede la valeur seuil predeterminee.  module exceeds the predetermined threshold value.

Le systeme de detection comporte au moins un moyen de mesure  The detection system comprises at least one measurement means

de vibration sur au moins un plan radial du moteur.  vibration on at least one radial plane of the engine.

L'invention a aussi pour objet un moteur d'aeronef comprenant un compresseur munis de premiers disques rotatifs et une turbine muni de seconds disques rotatifs, mettant en cauvre un systeme de detection defini ci avant. Selon un mode de realisation prefere, le systeme de detection comprend un premier moyen de mesure de vibration au niveau d'un des premiers disques rotatifs et un second moyen de mesure de vibration au  The invention also relates to an aircraft engine comprising a compressor provided with first rotary discs and a turbine provided with second rotary discs, making a poorly defined detection system defined above. According to a preferred embodiment, the detection system comprises a first vibration measuring means at one of the first rotary discs and a second means for measuring vibration at

niveau des seconds disques rotatifs.  level of the second rotating discs.

L'invention a aussi pour but un programme informatique conqu pour mettre en ceuvre le procede defini ci-avant lorsqu'il est execute par un ordinateur.  The invention also aims at a computer program designed to implement the method defined above when it is executed by a computer.

Breve description des dessinsBrief description of the drawings

L'invention sera mieux comprise a la lecture de la description faite  The invention will be better understood on reading the description made

ci-apres, a titre indicatif mais non limitatif, en reference aux dessins annexes, sur lesquels: - la figure est une vue d'un turboreacteur d'aeronef, comportant sch em atiquement u n system e de detection d'endom m agement de rotor se lon ['invention; - les figures 2A a 2C illustrent l'enregistrement de donnees relatives a la vitesse, I'amplitude et la phase respectivement, stockees pendant le vol par ['unite memoire selon ['invention; - la figure 3 est un organigramme illustrant, selon 1'invention le procede de detection d'endommagement de rotor d'un moteur d'aeronef; - la figure 4 montre une representation de vecteurs vibrations selon le procede de la figure 3; - la figure 5 illustre les amplitudes de vecteurs vibrations en fonction de la vitesse selon le procede de la figure 3; - les figures 6A et 6B illustrent des nuages de points representant les coordonnees cartesiennes des vecteurs vibrations et de leur vecteurs moyens respectivement, pour un intervalle de vitesse donnee selon le procededelafigure3; - les figures 7A et 7B illustrent des differences vectorielles entre des vecteurs moyens d'un vol de reference et les vecteurs moyens d'un vol determine selon le procede de la figure 3; - la figure 8 illustre un cercle limitant une zone seuil selon le procede de la figure 3; - les figures 9A et 9B illustrent des differences vectorielles entre des vecteurs moyens d'un vol de reference et les vecteurs d'un vol determine selon le procede de la figure 3; - la figure 10 est un organigramme illustrant, selon 1'invention le procede de detection d'endommagement de rotor d'un moteur d'aeronef au cours du vol; et  Hereinafter, by way of indication but not limitation, with reference to the accompanying drawings, in which: - the figure is a view of an aircraft turbojet, schematically comprising a system for detecting rotor damage in accordance with the invention; FIGS. 2A to 2C illustrate the recording of data relating to speed, amplitude and phase respectively, stored during the flight by the memory unit according to the invention; FIG. 3 is a flowchart illustrating, according to the invention, the method for detecting rotor damage of an aircraft engine; FIG. 4 shows a representation of vibration vectors according to the method of FIG. 3; FIG. 5 illustrates the vibration vector amplitudes as a function of the speed according to the method of FIG. 3; FIGS. 6A and 6B illustrate scatter plots representing the Cartesian coordinates of the vibration vectors and their mean vectors respectively, for a given velocity interval according to the procedure of FIG. FIGS. 7A and 7B illustrate vector differences between mean vectors of a reference flight and the mean vectors of a flight determined according to the method of FIG. 3; FIG. 8 illustrates a circle limiting a threshold zone according to the method of FIG. 3; FIGS. 9A and 9B illustrate vector differences between mean vectors of a reference flight and the vectors of a flight determined according to the method of FIG. 3; FIG. 10 is a flowchart illustrating, according to the invention, the method of detecting rotor damage of an aircraft engine during flight; and

Description detaillee de modes de realisation  Detailed description of embodiments

La figure montre une partie d'un moteur d'aeronef, plus particulierement d'un turboreacteur. Le turboreacteur comprend un compresseur basse pression et un compresseur haute pression 2 qui fournissent un debit d'air comprime a une chambre de combustion 3 afin d'assurer une combustion continue du combustible. Les gaz a haute pression et haute temperature s'echappent a grande vitesse par une tuyere (non representee). Les compresseurs vent entraines par une turbine 4 qui preleve et transforme une partie de l'energie du gaz comprime et chaud en une ,.  The figure shows part of an aircraft engine, more particularly of a turbojet. The turbojet comprises a low pressure compressor and a high pressure compressor 2 which provide a compressed air flow to a combustion chamber 3 to ensure a continuous combustion of the fuel. The gases at high pressure and high temperature escape at high speed through a nozzle (not shown). The wind compressors are driven by a turbine 4 which picks up and transforms a portion of the energy of the compressed and hot gas into one.

energle mecanlque.mechanical energy.

Chaque compresseur comprend une partie tournante ou rotor 5, une partie fixe ou stator 6 et une enveloppe ou carter 7. Le rotor comprend un tambour constitue par 1'assemblage de plusieurs disques, sur lesquels vent fixees des aubes mobiles 8. Le stator est constitue de plusieurs rangees  Each compressor comprises a rotating part or rotor 5, a stationary part or stator 6 and a casing or casing 7. The rotor comprises a drum constituted by the assembly of several disks, on which fixed blades 8 are fixed. The stator constitutes several rows

d'aubes fixes qui peuvent etre fixces sur le carter 7.  fixed vanes which can be fixed on the casing 7.

La turbine 4 comprend un ou plusieurs etages ou chaque etage se compose d'une grille d'aubes fixes 9a et d'une grille d'aubes mobiles 9b fixees  The turbine 4 comprises one or more stages or each stage consists of a fixed vanes grid 9a and a fixed blade vanes 9b fixed

sur un disque.on a disk.

En fonctionnement, les differentes aubes vent soumises aux efforts aerodynamiques. De plus, les aubes mobiles 8 et 9b vent soumises a la force centrifuge qui est proportionnelle au carre de la vitesse de rotation. Ainsi, les aubes et leur attache sur le disque vent dimensionnees pour les plus severes  In operation, the different vanes wind subjected to aerodynamic efforts. In addition, the blades 8 and 9b wind subjected to the centrifugal force which is proportional to the square of the speed of rotation. Thus, the blades and their attachment to the disc wind dimensioned for the most severe

conditions de fonctionnement.Working conditions.

L'aube etant une sorte de lamelle, peut vibrer a une frequence propre qui depend de sa forme, de ses dimensions et de son mode de fixation sur le disque. Ces vibrations peuvent etre excitees par des sillages qui naissent au bord de fuite des aubes, par des forces mecaniques prenant naissance dans le rotor lorsque celui-ci presente des balourds trop importants ou par des instabilites aerodynamiques. Par consequent, les vibrations entretenues qui en resultent peuvent entraner la rupture ou la perte d'une ou de  The dawn being a kind of lamella, can vibrate at a proper frequency that depends on its shape, its dimensions and its way of fixing on the disc. These vibrations can be excited by wakes which are born at the vanishing edge of the vanes, by mechanical forces originating in the rotor when it presents unbalanced imbalances or by aerodynamic instabilities. Consequently, the resulting sustained vibrations can result in the breakage or loss of one or

plusieurs aubes.several blades.

Ainsi, certains endommagements de pieces tournantes generent une modification brutale du balourd du rotor correspondent et par  Thus, certain damages of rotating parts generate a sudden modification of the unbalance of the rotor corresponding and by

consequent, de la vibration.therefore, vibration.

En generale, les vibrations de moteurs vent surveillees par des accelerometres ou autres capteurs de vibration. Chaque capteur peut etre compose de deux accelerometres faisant entre eux un angle, de preference de 90 , dans un plan radial du moteur. Les capteurs peuvent etre places sur le carter 7 au niveau de la turbine 4, de l'un des compresseurs 1, 2 ou entre ces compresseurs. Bien entendu, il est preferable que le capteur de vibration  In general, the vibrations of wind motors are monitored by accelerometers or other vibration sensors. Each sensor may be composed of two accelerometers forming an angle between them, preferably 90, in a radial plane of the engine. The sensors can be placed on the casing 7 at the turbine 4, one of the compressors 1, 2 or between these compressors. Of course, it is preferable that the vibration sensor

soit place en regard du ou des disques mobiles a surveiller.  place next to the mobile disk or disks to monitor.

La figure 1 montre schematiquement un premier capteur 12a de vibration, place au niveau du compresseur 2 et un second capteur 12b de vibration place au niveau de la turbine 4. Il est evident, que le nombre de  FIG. 1 schematically shows a first vibration sensor 12a, placed at the level of the compressor 2 and a second vibration sensor 12b placed at the level of the turbine 4. It is obvious that the number of

capteurs de vibrations peut etre quelconque et ieur emplacement peut varier.  Vibration sensors may be any and their location may vary.

De fason connue, chaque capteur de vibration fourni un signal electrique representatif des vibrations mecaniques du compresseur ou de la turbine. Apres amplification et filtration le signal est convert) en des donnees numeriques par un convertisseur analogique-numerique afin d'etre analyse  As is known, each vibration sensor provides an electrical signal representative of the mechanical vibrations of the compressor or the turbine. After amplification and filtration the signal is converted into digital data by an analog-digital converter in order to be analyzed

numeriquement.numerically.

En outre, un capteur 16 de vitesse mesure la vitesse de rotation du rotor associe au compresseur et il existe un autre capteur de vitesse (non  In addition, a speed sensor 16 measures the speed of rotation of the rotor associated with the compressor and there is another speed sensor (no

represente) qui mesure la vitesse de rotation du rotor associe a la turbine.  represents) the speed of rotation of the rotor associated with the turbine.

Comme le montre de fason tres schematique la figure i, le systeme de detection d'endommagement selon ['invention, comprend un systeme de traitement de donnees 22 comprenant de fason classique, une unite d'interface 23 qui resoit les donnees numeriques en provenance des capteurs et les transfere dans une unite memoire 25 akin que ces donnees soient traites par une unite centrale 24. Par ailieurs, le systeme de traitement est connecte a un ecran et/ou une imprimante, places par exemple dans le cockpit. Conformement a ['invention, les figures 2A a 2C illustrent un exemple d'enregistrement de donnees stockees pendant le vol par 1'unite  As shown schematically in FIG. 1, the damage detection system according to the invention comprises a data processing system 22 comprising a conventional form, an interface unit 23 which receives the digital data from the data sources. sensors and transferees in a unit memory 25 akin that these data are treated by a central unit 24. In addition, the processing system is connected to a screen and / or a printer, placed for example in the cockpit. In accordance with the invention, FIGS. 2A-2C illustrate an example of recording data stored during flight by the unit.

memoire 25.memory 25.

En effet, I'exemple de la figure 2A illustre un spectre 32 decrivant ['evolution de la vitesse N(t) du rotor en fonction du temps en secondes. Dans cet exemple, la vitesse est normalisee par rapport a la vitesse nominale et est  In fact, the example of FIG. 2A illustrates a spectrum 32 describing the evolution of the speed N (t) of the rotor as a function of time in seconds. In this example, the speed is normalized to the rated speed and is

donnee sous forme de pourcentage.given as a percentage.

La vibration v(t) est caracterisee par son amplitude A(t), ctest-a-  The vibration v (t) is characterized by its amplitude A (t), that is,

dire, par un ecart maximal par rapport a une position d'equilibre et par sa frequence ou pulsation rp(t). L'amplitude a done la dimension d'une longueur exprimee ici en micrometre ou en mils et la pulsation peut etre exprimee en radian/seconde ou en degre/seconde. D'une maniere generale la vibration est exprimee par une variable compiexe de module A(t) et d'argument p(t) en  ie, by a maximum deviation from an equilibrium position and by its frequency or pulsation rp (t). The amplitude therefore has the dimension of a length expressed here in micrometre or mils and the pulsation can be expressed in radian / second or in degree / second. In a general way the vibration is expressed by a compiexed variable of module A (t) and argument p (t) in

radians, de la forme v(t)=A(t)exp(i(p(t)).  radians, of the form v (t) = A (t) exp (i (p (t)).

Ainsi, a un instant donne une vibration est definie par une amplitude et par une phase ou angle. Les exemples des figures 2B et 2C illustrent 1'amplitude et la phase respectivement des vibrations enregistrees  Thus, at a given moment a vibration is defined by an amplitude and a phase or angle. The examples of FIGS. 2B and 2C illustrate the amplitude and the phase respectively of recorded vibrations.

pendant un vol determine.during a specific flight.

La figure 2B illustre ['evolution de ['amplitude A(t), en mils, en fonction du temps en secondes. Une premiere courbe 34a d'amplitude al(t)  Figure 2B illustrates the evolution of amplitude A (t), in mils, as a function of time in seconds. A first curve 34a of amplitude al (t)

represente les donnees mesurees par le premier capteur 12a de vibration.  represents the data measured by the first vibration sensor 12a.

Une seconde courbe 34b d'amplitude A2(t) represente les donnees mesurees  A second curve 34b of amplitude A2 (t) represents the measured data

par le second capteur 12b de vibration.  by the second vibration sensor 12b.

La figure 2C illustre ['evolution de la phase rp(t), en degree, en fonction du temps en secondes. Une premiere courbe 36a de phase cpl(t),  FIG. 2C illustrates the evolution of the phase rp (t), in degree, as a function of time in seconds. A first curve 36a of phase cpl (t),

represente les donnees mesurees par le premier capteur 12a de vibration.  represents the data measured by the first vibration sensor 12a.

Une seconde courbe 36b de phase p2(t), represente les donnees mesurees  A second curve 36b of phase p2 (t), represents the measured data

par le second capteur 12b de vibration.  by the second vibration sensor 12b.

A titre d'exemple, le taux d'acquisition des donnees des figures 2A a 2C, correspond a une donnee par seconde. Conformement a 11nvention, les figures 3 a 9B illustrent le procede de detection d'endommagement de rotor d'un moteur d'aeronef. Ce procede de detection peut etre realise en cours du vol d'aeronef ou a la suite de ce vol. La figure 3 est un organigramme illustrant ce procede de detection a la suite d'un vol determine. Le processus (voir aussi figure i) est mis en ceuvre au moyen de programmes stockes en memoire 25 du systeme de traitement 22. Le processus est demarre (etape 10) par la lecture de donnees relatives a la vitesse et a la vibration du rotor, stockees en memoire 25 pendant le vol. Ainsi, a ['issue de chaque vol. I'unite centrale lit la vitesse de rotation du rotor (figure 2A), I'amplitude (figure 2B) et la phase (figure 2C)  By way of example, the data acquisition rate of FIGS. 2A to 2C corresponds to one data per second. In accordance with the invention, Figures 3 to 9B illustrate the method of detecting rotor damage of an aircraft engine. This method of detection can be performed during the flight of aircraft or as a result of this flight. Fig. 3 is a flowchart illustrating this detection method following a specific flight. The process (see also FIG. 1) is implemented by means of programs stored in the processing system 22. The process is started (step 10) by reading data relating to the speed and vibration of the rotor, stored in memory during the flight. Thus, after each flight. The central unit reads the rotational speed of the rotor (FIG. 2A), the amplitude (FIG. 2B) and the phase (FIG. 2C)

des vibrations.vibrations.

A l'etape 20, la vibration a un instant donne t est exprimee par un vecteur vibration V defini a partir de ['amplitude A(t) et la phase cp(t) a cet  In step 20, the vibration has a given instant t is expressed by a vibration vector V defined from the amplitude A (t) and the phase cp (t) at this point.

instant t, de la vibration du rotor.  moment t, of the vibration of the rotor.

En effet, la figure 4 montre une representation a un instant donne des vecteurs vibrations V1 et V2, des premier et second capteurs respectivement, en coordonnees polaires. Les longueurs des vecteurs V! et V2 vent proportionnelles a leur modules Al et A2 et les angles qu'ils font avec  Indeed, Figure 4 shows a representation at a given instant vibration vectors V1 and V2, first and second sensors respectively, in polar coordinates. The lengths of the vectors V! and V2 wind proportional to their modules Al and A2 and the angles they make with

l'axe principal correspondent a leur phases cp1 et cp2 respectivement.  the main axis correspond to their phases cp1 and cp2 respectively.

A l'etape 30 (voir aussi figure 5), les vecteurs vibrations, emanant de chaque capteur de vibration, vent parametres en fonction de la vitesse du rotor. Ensuite le spectre de la vitesse du rotor est subdivise en une pluralite d'intervalles de vitesse et par consequent les vecteurs vibrations vent tries  In step 30 (see also Figure 5), the vibration vectors emanating from each vibration sensor, wind parameters as a function of the speed of the rotor. Then the spectrum of the rotor speed is subdivided into a plurality of velocity intervals and hence the vibration vectors wind sort

selon ces intervalles.according to these intervals.

La subdivision n'est pas forcement reguliere et ['amplitude de l'intervalle de vitesse peut correspondre a une valeur comprise entre i% et % de la vitesse nominale du rotor. Il est preferable d'affiner la subdivision 3 des vitesses elevees du rotor car la vibration, et par consequent le risque de perte d'aubes, est plus elevee. A titre d'exemple, pour des vitesses rotors normalisees entre 80% et 110%, on peut choisir des subdivisions ou intervalles d'une amplitude de 1%. Par ailleurs, il est avantageux d'elargir ['amplitude des intervalles lorsque les vitesses vent falbles et meme d'eliminer la partie inferieure du spectre de la vitesse, afin de ne pas surcharger la memoire et le temps de traitement des donnees. Par exemple, on peut faire une subdivision de 2% ou pl us a des vitesses rotors normal isees en dessous de 80% et d'eli miner la  The subdivision is not necessarily regular and the amplitude of the velocity interval may correspond to a value between i% and% of the nominal speed of the rotor. It is preferable to refine the subdivision 3 of the high speeds of the rotor because the vibration, and therefore the risk of blade loss, is higher. By way of example, for rotational speeds normalized between 80% and 110%, it is possible to choose subdivisions or intervals of an amplitude of 1%. On the other hand, it is advantageous to widen the amplitude of the intervals when the wind speeds are low and even to eliminate the lower part of the spectrum of the speed, so as not to overload the memory and the data processing time. For example, a subdivision of 2% or more can be made at rotational speeds normalized below 80% and

partie en dessous de 20%.part below 20%.

En effet, la figure 5 montre un exemple d'une distribution des amplitudes (en mile), des vecteurs, determinees a partir d'un des capteurs, en fonction de la vitesse normalisee du rotor. Dans cet exemple, le spectre de la vitesse du rotor est subdivise en des intervalles d'une amplitude de 2% et  Indeed, Figure 5 shows an example of a distribution of amplitudes (in miles), vectors, determined from one of the sensors, depending on the normalized speed of the rotor. In this example, the spectrum of rotor speed is subdivided into intervals of 2% amplitude and

dans un intervalle global compris entre 20% et 100% de la vitesse nominale.  in an overall range of between 20% and 100% of the rated speed.

A l'etape 40, les coordonnees du vecteur moyen <V> de vibration  At step 40, the coordinates of the average vibration vector <V>

vent calculees pour chaque intervalle de vitesse et pour chaque capteur.  calculated for each speed interval and for each sensor.

La figure 6A illustre un exemple d'un nuage de points representant les coordonnees cartesiennes de vecteurs des vibrations determinees a partir du premier capteur, pour un intervalle de vitesse donnee. En particulier, cette figure represente les vecteurs vibrations dans un intervalle de vitesse entre % et 82% de la vitesse nominale. Une moyenne vectorielle, definissant un vecteur moyen <V1> dans l'intervalle donne, peut etre determinee en calculant le barycentre du nuage de points. On notera que si le nombre de points representant les coordonnees des vecteurs est faible, il est preferable  FIG. 6A illustrates an example of a scatter plot representing the Cartesian coordinates of vibration vectors determined from the first sensor, for a given velocity interval. In particular, this figure represents the vibration vectors in a speed interval between% and 82% of the nominal speed. A vector average, defining an average vector <V1> in the given interval, can be determined by calculating the center of gravity of the point cloud. Note that if the number of points representing the coordinates of the vectors is small, it is preferable

pour une meilleure analyse, de ne pas tenir compte de ces points.  for a better analysis, to ignore these points.

De meme, la figure 6B represente les coordonnees cartesiennes de vecteurs des vibrations determinees a partir du second capteur ainsi que leur  Similarly, FIG. 6B shows the Cartesian coordinates of vectors of the vibrations determined from the second sensor as well as their

vecteur moyen <V2> dans un intervalle de vitesse donnee.  mean vector <V2> in a given velocity interval.

A l'etape 50, le vecteur moyen representant chaque interval le et  In step 50, the average vector representing each interval and

chaque capteur est stocke en memoire.  each sensor is stored in memory.

A partir de ltetape 50, I'evolution de ces vecteurs est analysee par  Starting from step 50, the evolution of these vectors is analyzed by

les etapes 613 81 et/ou par les etapes 62 a 82.  steps 613 and / or steps 62 to 82.

Ainsi, a l'etape 61, pour chaque intervalle de vitesse et pour chaque capteur, on calcul la difference vectorielle D entre le vecteur moyen <V1> d'un vol de reference et le vecteur moyen du vol determine, bien entendu pour le meme intervalle de vitesse. On notera que les vecteurs moyens <V1> representant des differents intervalles de vitesses du vol de reference vent prealablement stockes en memoire 25 du systeme de  Thus, in step 61, for each speed interval and for each sensor, the vector difference D between the average vector <V1> of a reference flight and the mean vector of the flight determined is calculated, of course for the same speed interval. It will be noted that the average vectors <V1> representing the different reference flight velocity intervals are previously stored in the memory of the flight system.

traitement 22 (voir figure 1).treatment 22 (see Figure 1).

Le vol de reference peut correspondre au vol precedent le vol determine. Par ailleurs, le vol de reference peut correspondre a un vol associe  The reference flight may correspond to the flight preceding the flight determined. In addition, the reference flight may correspond to a flight associated

a un moteur standard de reference, par exemple un moteur d'essai.  has a standard reference engine, for example a test engine.

La figure 7A illustre le calcul de la difference vectorielle D1 entre le vecteur moyen <Vld> du vol de reference, par exemple le vol precedent et le vecteur moyen <V1> du vol determine, c'est-3-dire du dernier vol. a partir des donnees stockees en memoire et relatives au premier capteur. De meme la figure 7B illustre le calcul de la difference vectorielle D2 relatif au second capteur. Dans le cas ou cette difference vectorielle, calculee a ltetape 61, depasse une zone critique autour des coordonnees du ve*eur moyen de reference, alors on peut diagnostiquer que le rotor a subi un  FIG. 7A illustrates the calculation of the vector difference D1 between the mean vector <Vld> of the reference flight, for example the previous flight and the average vector <V1> of the determined flight, that is to say of the last flight. from the data stored in memory and relating to the first sensor. Similarly, FIG. 7B illustrates the calculation of the vector difference D2 relative to the second sensor. In the case where this vectorial difference, calculated in step 61, exceeds a critical zone around the coordinates of the average reference veh, then it can be diagnosed that the rotor has undergone a

endommagement, par exemple une rupture d'aube.  damage, for example a break of dawn.

La figure 8 illustre un cercle ayant pour centre les coordonnees du vecteur moyen <Vd> de reference et pour rayon une valeur predeterminee selon ['emplacement du detecteur. Ainsi, si la difference vectorielle depasse la zone definie par le cercle C, on peut alors considerer qu'il y a endommagement du rotor. Afin de simplifier le critere de selection, on peut calculer le module de la difference vectorielle pour pouvoir le comparer a une  FIG. 8 illustrates a circle having as a center the coordinates of the average vector <Vd> of reference and for radius a predetermined value according to the location of the detector. Thus, if the vectorial difference exceeds the area defined by the circle C, then it can be considered that there is damage to the rotor. In order to simplify the selection criterion, the vector difference module can be calculated in order to compare it to a

valeur seuil predeterminee.predetermined threshold value.

Ainsi, a l'etape 71, on calcul le module d de chaque difference vectorielle D, c'est-a-di re, pour cheque interval le de vitesse. Ensuite, on  Thus, in step 71, the module d of each vector difference D is calculated, that is, for each speed interval. Then we

stocke les valeurs de ces modules en memoire a l'etape 81.  stores the values of these modules in memory at step 81.

Ensuite, a l'etape 90, on compare le module d de la difference vectorielle avec la valeur seuil predeterminee. Cette valeur seuil peut  Then, in step 90, the modulus d of the vector difference is compared with the predetermined threshold value. This threshold value can

correspondre a une valeur comprise entre 2 mils et 5 mils par exemle.  correspond to a value between 2 mils and 5 mils for example.

En effet, le capteur de vibration est plus sensible aux balourds du compresseur qu'a ceux de la turbine. Par ailleurs, la sensibilite des capteurs  Indeed, the vibration sensor is more sensitive to unbalance of the compressor than those of the turbine. In addition, sensor sensitivity

de vibration depend aussi du regime moteur.  vibration also depends on the engine speed.

A titre d'exempie, la sensibilite du capteur varie entre environ 200 cm. g/mils et 300 cm.g/mils, c'est-a-dire, qu'un balourd d'un moment  As an example, the sensitivity of the sensor varies between about 200 cm. g / mils and 300 cm.g / mils, that is, an unbalance of a moment

d'environ 200 cm.g correspond a une vibration d'une amplitude de 1 mils.  of about 200 cmg corresponds to a vibration of an amplitude of 1 mils.

En generale, une rupture d'aube se traduit par un balourd d'environ 2000 cm.g. Ainsi, en tenant compte d'un balourd residue! normal et des differentes sensibilites des capteurs, la rupture d'aube correspond a une variation d'amplitude de vibration de 2 mils a 5 mils. On notera que, la plage  In general, a break of dawn results in an unbalance of about 2000 cm.g. So, taking into account a residual imbalance! normal and different sensitivities of the sensors, the blade break corresponds to a vibration amplitude variation of 2 mils to 5 mils. It should be noted that, the beach

de variation de la valeur seuil peut varier selon le modele du moteur.  variation of the threshold value may vary depending on the motor model.

Un processus de calcul d'une dispersion statistique des vecteurs sera maintenant decrit en reference aux etapes 62 a 82. Ainsi, a l'etape 62 (voir aussi figures 9A et 9B) on calcui l'ecart type vectoriel de chaque vecteur, defini auparavant a ltetape 30 dans un intervalle de vitesse determine. Alors, on calcul dans cet intervalle de vitesse, la difference vectorielle entre chaque vecteur vibration V1 ou V2 (defini a l'etape 30) du vol determine et le vecteur vibration moyen <Vld> ou <V2d> (stocke prealablement en memoire) d'un vol de reference pour un meme intervalle de  A process for calculating a statistical dispersion of the vectors will now be described with reference to steps 62 to 82. Thus, in step 62 (see also FIGS. 9A and 9B) the vector standard deviation of each vector defined previously is calculated. at step 30 in a determined speed interval. Then, in this velocity interval, the vector difference between each vibration vector V1 or V2 (defined in step 30) of the determined flight and the average vibration vector <Vld> or <V2d> (previously stored in memory) is calculated. a reference flight for the same interval of

vitesse rotor.rotor speed.

On notera, qu'il est aussi possible de calculer a l'etape 62, la difference vectorielle entre chaque vecteur vibration (defini a l'etape 30) du vol determine et le vecteur vibration moyen (stocke en memoire a l'etape 50)  Note that it is also possible to calculate in step 62, the vector difference between each vibration vector (defined in step 30) of the determined flight and the average vibration vector (stored in memory at step 50)

du vol determine pour un meme intervalle de vitesse rotor.  of the determined flight for the same rotor speed interval.

Alors, on calcul a l'etape 72, le module de la difference vectorielle associee a chaque vecteur vibration et on determine le module maximal dmaxl ou dmax2. Ensuite le module maximal, c'est-a-dire, le plus grand mod u le associe a l'interval le de vitesse determine est stocke en memoire a  Then, in step 72, the module of the vector difference associated with each vibration vector is calculated and the maximum modulus d max1 or d max2 is determined. Then the maximum modulus, that is to say, the largest mod u associated with the determined velocity interval, is stored in memory a

ltetape 82.step 82.

Ensuite, 3 l'etape 90, on compare le plus grand module de  Then, in step 90, we compare the largest module of

l'intervalle de vitesse determine avec la valeur seuil predeterminee.  the determined speed interval with the predetermined threshold value.

Lorsqu'un plus grand module (stocke en memoire a l'etape 82) ou un module d'une difference vectorielle (stocke en memoire a l'etape 81) excede la valeur seuil predeterminee, un signal d'alerte est emis sur un ecran du cockpit ou sur une imprimante a ['attention du personnel de maintenance. Alors, un examen approprie du moteur doit etre realise avant  When a larger module (stored in memory at step 82) or a module of a vector difference (stored in memory at step 81) exceeds the predetermined threshold value, an alert signal is emitted on a screen. cockpit or on a printer to the attention of maintenance personnel. So, a proper examination of the engine must be done before

tout redemarrage.all restart.

Par ailieurs, lorsque le module ou le plus grand module de la difference vectorielle n'excede pas la valeur seuil predeterminee une mise a jour est realisee pour les vecteurs moyens du vol reference a partir des donnees du vol determine afin de tenir compte d'une evolution normale du moteur. Il est aussi envisageable que les donnees relatives a la vitesse et a la vibration du rotor soit stockees sur un support de stockage amovible afin de traiter ces donnees par un ordinateur au sol apres atterrissage de l'aeronef. Le procede de detection d'endommagement de rotor d'un moteur d'aeronef a la suite d'un vol determine est particulierement avantageux en ce que le pilote n'est pas perturbe par ce genre de problemes de moindre importance. Un autre avantage est le fait que le systeme de traitement au  On the other hand, when the module or the largest module of the vectorial difference does not exceed the predetermined threshold value, an update is performed for the average vectors of the reference flight from the data of the determined flight in order to take account of a normal evolution of the engine. It is also conceivable for the rotor speed and vibration data to be stored on a removable storage medium to process the data by a computer on the ground after landing the aircraft. The method of detecting rotor damage of an aircraft engine following a particular flight is particularly advantageous in that the pilot is not disturbed by such minor problems. Another advantage is the fact that the treatment system

bord de l'aeronef ne soit pas surcharge.  Aircraft edge is not overload.

Ceci dit, il est tout a fait possible de detecter l'endommagement du  That said, it is quite possible to detect the damage of the

rotor en cours du vol par un procede semblable a celui de la figure 3.  rotor during flight by a method similar to that of Figure 3.

En effet, les etapes de l'organigramme illustre a la figure 10 vent semblables a celui de la figure 3, sauf que le processus demarre a l'etape 110 par la lecture en temps reel de donnees relatives a la vitesse du rotor ainsi qu'a ['amplitude et a la phase des vibrations du rotor. A l'etape 120, la vibration est exprimee par un vecteur qui est defini par rapport a un intervalle de vitesse rotor determine (etape 130). En revanche, a l'etape 140, les coordonnees d'un vecteur moyen de vibration pour un intervalie de vitesse  In fact, the steps of the flowchart illustrated in FIG. 10 are similar to those of FIG. 3 except that the process starts at step 110 by reading in real time data relating to the speed of the rotor as well as amplitude and phase of rotor vibration. In step 120, the vibration is expressed by a vector that is defined with respect to a determined rotor speed interval (step 130). On the other hand, in step 140, the coordinates of a mean vector of vibration for a speed interval

determine est calcule a partir des donnees partielles requises a l'etape 110.  determined is calculated from the partial data required in step 110.

Ainsi, le vecteur moyen peut evoluer au cours du vol en s'enrichissant des donndes ult6heums. A letups 150, chaque velour mien calculi em stocks en m6moire en Fumigant 6ventueVement le voyeur mien, prAcAdemment stocky et relaUf au mime intense de vResse. gums lea autos grapes scat  Thus, the average vector can evolve during the flight by enriching itself with subsequent data. At 150, each velvet mine calculates memory in the event of possibly fogging the voyeur mine, prAcemment stocky and relaUf the intense mime of speed. gums lea autos grapes scat

semblables Sues gushes pcAdemment Dgum 3.  similar Sush gushes pcAdemment Dgum 3.

ss

Claims (16)

REVENDICATIONS 1. Procede de detection d'endommagement de rotor d'un moteur d'aeronef comprenant des moyens de mesure de vibration et de vitesse du rotor pendant un vol determine, caracterise en ce qu'il comporte les etapes suivantes: - acquisition de donnees relative a la vitesse du rotor ainsi qu'3 ['amplitude et a la phase des vibrations du rotor a partir desdits moyens de mesure, - calcul d'un vecteur vibration moyen sur un intervalle de vitesse de rotor determine a partir desdites donnees acquises, - calcul d'une difference vectorielle entre le vecteur vibration moyen audit vol determine et le vecteur vibration moyen d'un vol de reference pour un meme intervalle de vitesse rotor, - comparaison du module de ladite difference vectorielle avec une valeur seuil predetermine, et - emission d'un signal d'alerte lorsque le module de ladite  1. Method for detecting rotor damage of an aircraft engine comprising means for measuring vibration and rotor speed during a given flight, characterized in that it comprises the following steps: - acquisition of relative data at the rotor speed as well as the rotor amplitude and vibration phase from said measuring means; calculating a mean vibration vector over a given rotor speed interval from said acquired data; calculating a vector difference between the average vibration vector at said determined flight and the average vibration vector of a reference flight for the same rotor speed interval, - comparing the modulus of said vector difference with a predetermined threshold value, and - emission an alert signal when the module of the difference vectorielle excede une valeur seuil predeterminee.  vector difference exceeds a predefined threshold value. 2. Procede de detection selon la revendication 1, caracterise en ce qu'il comporte en outre, les etapes suivantes: - calcul d'une deuxieme difference vectorielle entre chaque vecteur vibration audit vol determine et le vecteur vibration moyen d'un vol de reference pour un meme intervalle de vitesse rotor, - calcul d'un module de ladite deuxieme difference vectorielle associee a chaque vecteur vibration afin de choisir un plus grand module, - comparaison audit plus grand module avec la valeur seuil predeterminee, et - emission d'un signal d'aierte lorsque ledit plus grand module  2. Detection method according to claim 1, characterized in that it further comprises the following steps: calculating a second vector difference between each vibration vector at said determined flight and the average vibration vector of a reference flight for a same rotor speed interval, - calculating a module of said second vector difference associated with each vibration vector in order to choose a larger module, - comparing to said larger module with the predetermined threshold value, and - transmitting a warning signal when said larger module excede la valeur seuil predeterminee.  exceeds the predetermined threshold value. 3. Procede de detection selon la revendication i, caracterise en ce qu'il comporte en outre, les etapes suivantes: - calcul d'une troisieme difference vectorielle entre chaque vecteur vibration audit vol determine et le vecteur vibration moyen audit vol determine 3 un meme intervalle de vitesse rotor, - calcul d'un module de ladite troisieme difference vectorielle associee a chaque vecteur vibration afin de choisir un plus grand module, - comparaison audit plus grand module avec la valeur seuil predeterminee, et - emission d'un signal d'alerte lorsque ledit plus grand module  3. Detection method according to claim 1, characterized in that it further comprises the following steps: - calculation of a third vector difference between each vibration vector at said determined flight and the average vibration vector at said flight determined 3 a same rotor speed interval, - calculating a module of said third vector difference associated with each vibration vector in order to choose a larger module, - comparing said larger module with the predetermined threshold value, and - transmitting a signal of alert when said larger module excede la valeur seuil predeterminee.  exceeds the predetermined threshold value. 4. Procede de detection selon l'une quelconque des revendications  4. Detection method according to any one of the claims 1 a 3, caracterise en ce que lesdites etapes de calcul, de comparaison et  1 to 3, characterized in that said steps of calculation, comparison and d'emission vent realisees a ['issue audit vol determine.  issued at the end of the said determined flight. 5. Procede de detection selon l'une quelconque des revendications  5. Detection method according to any one of the claims a 3, caracterise en ce que le procede de detection est realise en cours audit  a 3, characterized in that the detection method is carried out during the audit vol determine.determined flight. 6. Procede de detection selon l'une quelconque des revendications  6. Detection method according to any one of the claims a 5, caracterise en ce que le vol de reference correspond au vol precedent  a 5, characterized in that the reference flight corresponds to the preceding flight audit vol determine.determined flight audit. 7. Procede de detection selon l'une quelconque des revendications  7. Detection method according to any one of the claims a 5, caracterise en ce que le vol de reference correspond 3 un vol associe a  a 5, characterized in that the reference flight corresponds to a flight associated with un moteur standard de reference.a standard reference engine. 8. Procede de detection selon l'une quelconque des revendications  8. Detection method according to any one of the claims a 6, caracterise en ce qu'il comporte en outre une etape de mise a jour des vecteurs moyens du vol reference a partir des donnees audit vol determine lorsque le module ou le plus grand module de la difference vectorielle  a 6, characterized in that it further comprises a step of updating the mean vectors of the reference flight from the data of said determined flight when the module or the largest module of the vectorial difference n'excede pas la vaieur seuil predeterminee.  does not exceed the predefined threshold value. 9. Procede de detection selon l'une quelconque des revendications  9. Detection method according to any one of the claims 1 a 8, caracterise en ce que ['amplitude audit intervalle de vitesse rotor determine correspond a une valeur comprise entre 1% et 10% de la vitesse  1 to 8, characterized in that the amplitude at said determined rotor speed interval corresponds to a value between 1% and 10% of the speed nominale du rotor.nominal rotor. 10. Procede de detection selon l'une quelconque des  10. Detection method according to any one of revendications 1 a 9, caracterise en ce que la valeur seuil est predeterminee  Claims 1 to 9, characterized in that the threshold value is predetermined selon ltemplacement du moyen de detection de vibration et correspond a une  according to the location of the vibration detection means and corresponds to a valeur comprise entre 2 mils et 5 mils.  value between 2 mils and 5 mils. 11. Systeme de detection d'endommagement de rotor d'un moteur d'aeronef muni des moyens de mesure de vibration et de vitesse du rotor pendant un vol determine, caracterise en ce qu'il comprend: - un moyen d'acquisition de donnees relative a la vitesse du rotor ainsi qu'a ['amplitude et a la phase des vibrations du rotor a partir desdits moyens de mesures, - un moyen de calcul d'un vecteur vibration moyen sur un intervalle de vitesse de rotor determine a partir desdites donnees acquises, - un moyen de calcul d'une difference vectorielle entre le vecteur vibration moyen audit vol determine et le vecteur vibration moyen d'un vol de reference pour un meme intervalle de vitesse rotor, - un moyen de comparaison du module de ladite difference vectorielle avec une valeur seuil predetermine, et - un moyen d'emission d'un signal d'alerte lorsque le module de  11. System for detecting rotor damage of an aircraft engine provided with means for measuring vibration and rotor speed during a given flight, characterized in that it comprises: a means of data acquisition relating to the speed of the rotor and the amplitude and phase of rotor vibration from said measuring means; means for calculating a mean vibration vector over a given rotor speed interval from said rotor; acquired data; means for calculating a vector difference between the average vibration vector at said determined flight and the average vibration vector of a reference flight for the same rotor speed interval; means for comparing the module of said difference vector with a predetermined threshold value, and - a means of transmitting an alert signal when the module of ladite difference vectorielle excede une valeur seuil predeterminee.  said vector difference exceeds a predetermined threshold value. 12. Systeme de detection selon la revendication 11, caracterise en ce qu'il comprend en outre: - un moyen de calcul d'une deuxieme difference entre chaque vecteur vibration audit vol determine et le vecteur vibration moyen d'un vol de reference pour un meme intervalle de vitesse rotor, - un moyen de calcul d'un module de ladite deuxieme difference vectorielle associee a chaque vecteur vibration et de choisir un plus grand module, un moyen de comparaison audit plus grand module avec la valeur seuil predeterminee, et - un moyen d'emission d'un signal d'alerte lorsque ledit plus grand  12. Detection system according to claim 11, characterized in that it further comprises: a means for calculating a second difference between each vibration vector at said determined flight and the average vibration vector of a reference flight for a same rotor speed interval; means for calculating a module of said second vector difference associated with each vibration vector and for selecting a larger module; means for comparing said largest module with the predetermined threshold value; and means of transmitting an alert signal when said larger module excede la valeur seuil predeterminee.  module exceeds the predetermined threshold value. 13. Systeme de detection selon la revendication 11, caracterise en ce qu'il comporte en outre, les etapes suivantes: - un moyen de calcul d'une troisieme difference vectorielle entre chaque vecteur vibration audit vol determine et le vecteur vibration moyen audit vol determine a un meme intervalle de vitesse rotor, - un moyen de calcul d'un module de ladite troisieme difference vectorielle associee 3 chaque vecteur vibration afin de choisir un plus grand module, - un moyen de comparaison audit plus grand module avec la valeur seuil predeterminee, et - un moyen d'emission d'un signal d'alerte lorsque ledit plus grand  13. Detection system according to claim 11, characterized in that it further comprises the following steps: a means for calculating a third vector difference between each vibration vector at said determined flight and the average vibration vector at said determined flight has a same rotor speed interval, - means for calculating a module of said third associated vector difference 3 for each vibration vector in order to choose a larger module, - comparator means for said larger module with the predetermined threshold value, and - means for transmitting an alert signal when said larger module excede la valeur seuil predeterminee.  module exceeds the predetermined threshold value. 2514. Systeme de detection selon l'une quelconque des  2514. A detection system according to any one of revendications 11 3 13, caracterise en ce qu'il comporte au moins un moyen  claims 11 3 13, characterized in that it comprises at least one means de mesure de vibration sur au moins un plan radial du moteur.  measuring vibration on at least one radial plane of the engine. 15. Moteur d'aeronef comprenant un compresseur munis de premiers disques rotatifs et une turbine muni de seconds disques rotatifs, caracterise en ce qu'il comporte un systeme de detection selon les  15. Aircraft engine comprising a compressor provided with first rotary discs and a turbine provided with second rotary discs, characterized in that it comprises a detection system according to the revendications 113 14.claims 113 14. 16. Poseur dmnef salon revendlcaBon 15, camris6 en ce qua is shame de diteion comprend an premier mown de mesure de vibration au Bateau don des premiers dlsques roach et an second moyen de  16. Reservoir living room dealer Good 15, built in that shame of dition includes first mown of measurement of vibration to the Boat don of the first darts roach and second means of mesure de vibration au nlveau des sends aquas rotas.  measurement of vibration at the level of sends aquas rotas. s 17. Programme lnrmadque carat en ce qua eat conga pour medre en Louvre le procAdA sewn [une quelconque des mvendlcaBons 1 10  17. Program lnrmadque carat in the conquest of the Louvre for the trial of any one of the United States.
FR0206530A 2002-05-28 2002-05-28 METHOD AND SYSTEM FOR DETECTING ROTOR DAMAGE OF AN AIRCRAFT ENGINE Expired - Fee Related FR2840358B1 (en)

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FR0206530A FR2840358B1 (en) 2002-05-28 2002-05-28 METHOD AND SYSTEM FOR DETECTING ROTOR DAMAGE OF AN AIRCRAFT ENGINE
DE60307926T DE60307926T2 (en) 2002-05-28 2003-05-23 Method and system for detecting rotor damage in an aircraft engine
EP03291230A EP1367226B1 (en) 2002-05-28 2003-05-23 Method and system for damage detection of an aircraft engine rotor
ES03291230T ES2269942T3 (en) 2002-05-28 2003-05-23 PROCEDURE AND SYSTEM OF DETECTION OF FAULTS OF THE ROTOR OF AN AIRCRAFT ENGINE.
RU2003116164/06A RU2320969C2 (en) 2002-05-28 2003-05-26 Method and system of finding faults in flying vehicle engine rotor and flying vehicle engine
JP2003149102A JP4111869B2 (en) 2002-05-28 2003-05-27 Method and system for detecting damage to an aircraft engine rotor
UA2003054893A UA82462C2 (en) 2002-05-28 2003-05-28 Method and system for detecting damage to the rotor of an aircraft engine
CA2430153A CA2430153C (en) 2002-05-28 2003-05-28 Process and system for detecting aircraft engine rotor damage
US10/445,935 US6918747B2 (en) 2002-05-28 2003-05-28 Method and system for detecting damage to the rotor of an aircraft engine

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